US2623383A - Apparatus for calibrating the airspeed indicator of aircraft - Google Patents

Description

Dec. 30, 1952 J. E. BEVINS APPARATUS FOR CALIBRATING THE AIR-SPEED INDICATOR OF AIRCRAFT 5 Sheets-Sheet 1 Filed March 7, 1945 INVENTOR.

3 Jqulzes E. Bevilus.

NW QN FTI'URNEY J. E. BEVINS 2,623,383 APPARATUS FOR CALIBRATING THE AIR-SPEED INDICATOR OF AIRCRAFT 3 Sheets-Sheet 2 grwa/wtom lancesLKBevizc-s Dec. 30, 1952 Filed March 7, 1945 Dec. 30, 1952 J. E.-BEVINS 2,623,333

APPARATUS FOR CALIBRATING THE AIR-SPEED INDICATOR OF AIRCRAFT Filed March 7, 1945 s Sheets-Sheet 3 IN VEN TORL AT TORNE Y Jwlces E. Bevins.

Patented Dec. 30, 1952 APPARATUS FOR CALIBRATING THE AIR- SPEED INDICATOR OF AIRCRAFT James E. Bevins, Ramsey, N. J., assignor to Ben dix Aviation Corporation, Teterboro, N. .L, a

corporation of Delaware Application April 7, 1945, Serial No. 587,033

2 Claims. (01. 73-1) This invention relates to devices for the accurate measurement of air speed and more par- .night or under conditions of poor visibility. Un-

der these latter circumstances it is obvious that more precise formation flying may be had if the 'air speed indicators of all the craft are similarly calibrated and all readings follow the same curve.

The present invention accordingly has for one of its objects the provision of a master air speed indicator which may be readily employed as a test device so that the air speed indications thereof may be used to calibrate the usual air speed indicator of the aircraft.

Another object of the present invention is to provide a master air speed indicator capable of ready use on different aircraft, so that the airspeed measuring devices of all the aircraft may be quickly calibrated in accordance with the readings obtained from the master indicator.

Still another object is to provide a master indicator of the above type which embodies a novel construction permitting the sametoe readily suspended from the craft for the purpose of air speed determination, the arrangement being electrically operable in order that the indications may be observed upon an instrument positioned within the craft.

A further object comprehends an electrically operated Pitot tube which is suspended in the airstream below the craft to automatically align itself with the true flight path of the craft, to-

an arrangement permitting the balance of the trailing Pitot tube about its axis of suspension to be easily and quickly adjusted, so that the tube 2 will seek automatic alignment in the air stream during flight.

A still further object includes a novel and compact arrangement of parts including the provision of a highly desirable and effective calibrating mechanism for the dynamically operated diaphragm of the Pitot tube, the arrangement being such that extreme accuracy of calibration may be secured.

Another object is to provide an electrically operated master Pitot tube characterized by a novel arrangement of parts whereby the unit may be quickly associated with different aircraft to enable rapid and accurate calibration of the air speed indicators thereof.

Other objects and novel features of the invention will appear more fully hereinafter from the following detailed description when taken in connection with the accompanying drawings wherein one form of the invention is illustrated. It is to be expressly understood, however, that the drawings are utilized for purposes of illustration only and are not designed as a definition of the limits of the invention, reference being had for this purpose to the appended claims.

Referring more particularly to the drawings wherein similar reference characters refer to similar parts throughout the several views;

Figure 1 is a side view partly in section of an electrically operated Pitot tube mechanism for the indication of air speed and constructed in accordance with the principles of the present invention;

Figure 2 is an enlarged view partly in section of the transmitter unit and operating parts associated therewith;

Figure 3 is an end view of the transmitter unit showing the calibrating spring which is associated with the diaphragm;

Figure 4 is a view similar to Figure 2 but taken at right angles to the latter and illustrating the cooperation between the diaphragm and transmitter;

Figure 5 is an enlarged detail showing the manner of sealing the transmitter unit in the Pitot tube casing;

Figure 6 is a sectional view taken along lines 6-6 of Figure l; and

Figure '7 is a fragmentary view in section taken along lines 1-! of Figure 1.

through an opening .32 in a cap 3 Referring more particularly to Figure l, the present invention is illustrated therein as comprising a Pitot tube It having a streamlined contour and adapted to be suspended from the aircraft as by means of the combined cable and electrical conduit I2. The Pitot tube I is provided in its forward portion with a suitable type of selfsynchronous telemetric transmitter 14 arranged to respond to variations in air speed, a selfsynchronous telemetric receiver It being located within the craft for observing the air speed of the Pitot tube and hence the airplane. A suitable source of electrical energy l8, within the craft may be readily and detachably connected with the self-synchronous telemetric system through the T-connection 28, and the entire assembly may be anchored to the craft by th'e"steel'cable*22 and hook 212.

In order that the Pitot tube it may respond to the variable air pressure during flight, for the purpose of measuring the air speed, the forward portion, or nose 2 is provided with a centrally disposed opening 26 for conveying dynamic pressure into casing 28 where it isconducted to the left side of a diaphragm 38 (Fig. l) Cap 3 5 securely clamps the diaphragm 38 to'a cylindrical support 3t which extends rearwardly and constitutes a rigid and stable mounting 38 for 'ments of the diaphragm maybe utilized for the purpose of measuring the air speed of the Pitot tube and hence the air speed of the plane from "which it is suspended.

Means are provided for interconnecting the diaphragmdil and the transmitter M, and in the form of the invention illustrated, such means is constituted by an arm 42, Figures'2 and 4,

pivotally secured at one end tothe central portion of the diaphragm 3d, and at the other end to an oscillatableshaft M through a lever 46. Preferably, lever 4'5 maybe adjusted with respect to arm 42 by means of a pin or screw 41 which may be inserted in one of a plurality of openings 48 in the'arm 32, this construction enabling adjusting movement of the shaft 44 relative to'the diaphragm 39 to be effected. A gear segment 5b, in constant meshing engagement with apinion 52 of the rotor of the transmitter M, is secured to the shaft 45, and is normally urged to the position shown in Figure 2 by 'a spring 54 anchored to the support 3%. If desired, a further adjustment for the shaft M and'gear-segment 50 may be provided by the cam screw 55, which when rotated, may vary the initial position of the gear segment 50 and hence the rotor "of the transmitter M.

A novel arrangement is provided by thetpresent invention for supporting the Pitot'tube W at its center of gravity to enable slight pivotal movement thereof to facilitate alignment of the tube in the flight path. As shown, such means include a supporting block 53 positioned within a recess 60 formed in a member 62, a pin 64 being inserted through the block and through suitable openings in the wall of the casing 28, see Figures 1 and '7. Preferably, the ends of the pin 64 are secured to the casing 23 and the block 53 pivotally moves about the axis of the pin. However, it will be understood that the block may be secured to the pin, if desired, in which event the ends of the latter are mounted to pivot in the walls of the casing 28. It is pointed out that the block 58 also constitutes a portion of the combined electrical and strain coupling 36 which contains suitable complementary pin type coupling members to connect cable I06 with the source It and indicator receiver it. With such an arrangement it will be readily perceived that the entire Pitot tube I0 is pivotally supported at its center of gravity through the block 58 and pin M, so that jthetubemayreadily balance and adjust itself in the proper flight path during operation.

In assembling the transmitter unit I l within the casing 23 of the Pitot tube, a novel construction is employed for securely maintaining the unit in position against lateral and longitudinal displacements and for effectively sealing the dynamic section of the unit from the static section thereof. In the form illustrated, the transmitter unit it is provided with .a support 68 which bears against a shoulder it .of1the casing i Q, as the unit is moved inwardly through the open forward portion of the tube. Thereafter, a deformable sealing ring l2, which ,may be formed of rubber, is placed in engagementwith a beveled forward face 13 of the unit 14, and the nose 2-; is assembled on the threaded open end of the tube, a pair of collars 14, is being interposed betweenthe nose 24 andthei'se'aling ring '52, for expanding thering against the inner wall of the casing 28 and for forcing the unit It inwardly against the shoulder it. Thus, the transmitter unit may be readily assembled in the forward portion of the Pitot'tube, and secured therein against lateral and longitudinal displacements, it being pointed out that'the support 36 snugly fits within the interior of the casing 28 and that the sealing ring forms a relatively simple but effective seal between the dynamic and static sections of the unit on opposite sides of the diaphragm 30.

in order that the Pitot tube may maintain a straight line flight path during flight, the rear portion thereof is provided with a suitable tailpiece 78. It is also pointed out that the casing "28 is provided on opposite sides of the member 62, with sections 88 and 82 Ma suitable mesh alloy in order to seal the tube'on either side of its pivotal support and provide proper weight distribution for efflcient operation. A further important feature in this respect includes a novel balancing means for securing accurate balance of the tube ll), after assembly, and at any subsequent period when the tube is not precisely balanced about the pin 64. As shown, such means comprises a metallic block 8 1 located at the rear portion of the tube andprovide'd with a bore 86 for receiving a locking pin 88 which is prevented from turning within the bore by virtue of a conventional key provided within the bore and engaging the pin. An adjustment screw 99, threadedly received by the block 84 is adapted to engage the beveled top 32 of the pin 88, this construction enabling the opposite end of the pinto be forced into tight frictional engagement with the inner wall of the casing to secure the block in any desired position of adjustment. Thus, if balancing of the tube is required, it is only necessaryito loosen the screw 90, move the block 84 to the proper position to secure balance, and tighten the screw to lock the block in the new position. Since the tailpiece 13 is readily removable from the tube by the use of fastening screws 96, it will be seen that the aforementioned adjustment may be quickly effected.

A further important feature of the invention includes the provision of a novel means for calibrating the diaphragm 30, in order to accurately position the same initially and in order also to secure accurate response thereof to different air speeds over a wide range. As shown, such means comprises a fiat-spiral spring 96 made of relatively thin spring metal, one end of the spring being secured, as by means of screws 98, to the cap 34, while the opposite end is secured to the center of the diaphragm 30 through a rod I00, Figures 2, 3 and l. Positioned between the spring 96 and the cap 34 are a plurality of studs I02 which are threadedly received in the cap 34, and provided with rounded heads I04 which may be selectively engaged with the spring to urge the latter away from the cap to variably tension the diaphragm as the studs are adjusted. With this construction, and as will be readily observed from Fig. 3, adjustment of the studs will serve to vary the effective length of the spring 96 and hence its rate, in its action in tensioning or calibrating the diaphragm 30 throughout its entire range of operation. If desired suitable wires may be associated with the studs H12 in order to secure them in their adjusted position. This structure is claimed in divisional application Serial No. 285,178, filed April 30, 1952.

As heretofore stated, the transmitter and receiver units In and 16 may be of any suitable electrically operated self-synchronous telemetric type wherein motion of the transmitter is synchronously reproduced at the receiver. A convenient system of this character which may be utilized in the present invention is that disclosed in the patent to Paul F. Bechberger, No. 2,342,637, dated February 29, 1944. The arrangement shown in this patent is especially desirable since it does not involve the use of contact brushes which would tend to introduce frictional loads and resultant errors in the electrical transmission of the relatively small torques involved'in an instrument such as an air speed indicator. However, it will be understood that other types of synchronous telemetric systems may be employed if desired, the primary requirement being that the receiver I6 reproduce at a remote point, the motion of the diaphragm 30. In the present invention, the transmitter unit I4 is provided with the required electrical connections, as well understood, and these connections form a cable I06 which is passed beneath the block 58, Figure l, and proceeds to the coupling 66 from whence it is associated with the source l8 and indicator It.

In operation, it is assumed that the Pitot tube in has been properly balanced and calibrated and it is desired to employ the instrument to calibrate the usual air speed indicators on one or more aircraft. Hook 24 is then anchored to the craft, and source I8 and indicator 16 are connected through detachable connections with the T coupling 20. With the craft in flight, the Pitot tube is then allowed to descend beneath the plane and be suspended therefrom through the cable i2, it being pointed out, that the latter is of sufiicient length so that the tube is free of any air disturbances caused by flight of the craft. The tube will thereupon assume the proper flight path ,attitudeas it is towed by the craft and the transmitter 14 will respond to variations in movement of the diaphragm 30, the latter being influenced by the differential of dynamic and static pressures acting thereon. All motion of the transmitter 14 will be conveyed to thereceiver 16, as heretofore described, and the readings of the latter, at different air speeds are employed for calibrating the crafts air speed indicator.

Once the air speed indicator on a particular craft has been calibrated, it is only necessary to repeat the process on the other craft, using the present invention as the master calibrating unit. Thus, all air speed indicators of all the aircraft of the squadron or fleet will have identical readings under similar air speed conditions and proper formation flying will be more readily attainable, especially under conditions of poor visibility.

The present invention thus affords a simple and effective means for calibrating the air speed indicators of one or more aircraft and. includes a novel structure which While relatively simple in construction, is exceedingly accurate and reliable in operation.

While a preferred embodiment of the invention has been disclosed herein, and described with considerable particularity, it will be understood by those skilled in the art, that the same is not limited thereto but may receive a variety of expressions without departing from the spirit of the invention. Reference will therefore be had to the appended claims for a definition of the limits of the invention.

What is claimed is:

1. In a device for indicating air speed, an elongated streamlined casing having a rounded nose portion and an outwardly flaring tail portion, air speed responsive means housed within the forward portion of said casing, means for pivotally supporting said casing at the center of gravity thereof, said means including a cable adapted to be secured to an aircraft whereby the casing may be suspended to trail therefrom, a weight movable within the rear portion of the casing for balancing the casing with respect to the supporting means, a pin carried by the weight for movement transversely thereof into frictional engagement with the inner wall of the casing, and an adjusting screw carried by the weight for so moving said pin as to fix the weight in any desired position of adjustment.

2. A Pitot tube for the determination of air speed comprising an elongated streamlined casing having an air speed responsive device including a diaphragm housed within the casing, a self-synchronous electrical transmitter within the casing and operatively connected with the diaphragm for generating signals responsive to the movements of the diaphragm, a pivot pin positioned in the casing at the center of gravity thereof, a support member connected to said pin to enable slight pivotal movement of the casing about said member, the latter having a hollow portion above the pin, an elongated hollow cable detachably connected with said member for suspending the casing below an aircraft in flight, a self-synchronous electrical receiver adapted to be positioned within the aircraft, and electrical circuit connections interconnecting said transmitter and receiver and including parts passing through said hollow portion of the support member and the hollow cable.

JAMES E. BEVINS.

(References on following page)

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